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Non-isocyanate curing system propellant and preparation method thereof

A non-isocyanate and propellant technology, applied in the direction of explosives, etc., can solve the problems that cannot meet the requirements of high-performance weapon systems, less research on interface enhancement, and low mechanical properties of propellants, so as to eliminate residual thermal stress and improve Mechanical properties, the effect of improving mechanical properties

Active Publication Date: 2020-07-14
HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, research at home and abroad generally pays attention to the construction of non-isocyanate curing system, and there are few studies on the interface enhancement between matrix and filler in non-isocyanate curing system propellants, resulting in the general mechanical properties of non-isocyanate curing system propellants filled with a large amount of solids. Low, unable to meet the demanding conditions of use of high-performance weapon systems
[0005] At present, the main method to improve mechanical properties is to add bonding agents, but the existing bonding agents are generally suitable for polyurethane curing systems, and cannot play a role in azide / alkyne curing bodies. Due to the lack of effective mechanical additives, non-isocyanate Cured system propellants have low mechanical properties

Method used

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  • Non-isocyanate curing system propellant and preparation method thereof
  • Non-isocyanate curing system propellant and preparation method thereof
  • Non-isocyanate curing system propellant and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0052] (1) prepare terminal alkyne group neutral polymer bonding agent, its infrared spectrogram is as figure 1 shown;

[0053] (a) dissolving the hydroxyl-terminated neutral polymer bonding agent NBPA in tetrahydrofuran to obtain a solution, and adding sodium hydride in proportion to the solution in a nitrogen atmosphere, wherein the molar percentage of NBPA and sodium hydride is 1:4;

[0054] (b) Move the mixed solution obtained in step (a) into a constant temperature reaction bath at 30° C., and the reaction time is 4 hours;

[0055] (c) The reactant obtained in step (b) is moved into an ice-water bath, and after the temperature is balanced, propyne bromide is added dropwise in proportion, and the molar ratio of propyne bromide to sodium hydride is 1:1.5;

[0056] (d) Seal the reactant obtained in step (c) with nitrogen gas, and move the reaction system into a temperature environment of 20°C, and continue to react at 20°C for 48h;

[0057] (e) filtering the reactant obtaine...

Embodiment 2

[0076] (1) Propellant formula composition (mass percentage %):

[0077]

[0078] (2) Propellant performance:

[0079] Theoretical standard specific impulse: 2657.8N.s / kg (271.2s)

[0080] Blank formula mechanical properties:

[0081] Maximum tensile strength σ at 20°C m =0.38MPa, maximum elongation ε m =102.8%

[0082] Maximum elongation at 70℃ε m =35.9%

[0083] -40℃maximum elongationε m = 38.7%

[0084] Mechanical properties after adding combined bonding agent:

[0085] Maximum tensile strength σ at 20°C m =0.57MPa, maximum elongation ε m =79.6%

[0086] Maximum elongation at 70℃ε m =46.7%

[0087] -40℃maximum elongationε m =48.4%

Embodiment 3

[0089] (1) Propellant formula composition (mass percentage %):

[0090]

[0091] (2) Propellant performance:

[0092] Theoretical standard specific impulse: 2655.8N.s / kg (271s)

[0093] Blank formula mechanical properties:

[0094] Maximum tensile strength σ at 20°C m =0.41MPa, maximum elongation ε m =95.7%

[0095] Maximum elongation at 70℃ε m = 37.9%

[0096] -40℃maximum elongationε m =40.1%

[0097] Mechanical properties after adding combined bonding agent:

[0098] Maximum tensile strength σ at 20°C m =0.61MPa, maximum elongation ε m =79.6%

[0099] Maximum elongation at 70℃ε m =48.3%

[0100] -40℃maximum elongationε m =50.4%

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Abstract

The invention relates to a non-isocyanate curing system propellant and a preparation method thereof, and belongs to the technical field of solid propellants. The non-isocyanate curing system propellant provided by the invention not only has good mechanical properties, but also has relatively high energy properties, the energy level of the propellant is equivalent to that of an NEPE high-energy solid propellant used by American strategic missiles, and the theoretical standard specific impulse of the propellant is greater than 270s. The problem that a non-isocyanate curing system propellant is poor in mechanical property is solved, the normal-temperature tensile strength, the high-temperature maximum elongation and the low-temperature maximum elongation of the propellant can be improved, andmeanwhile the process, safety and energy performance of the propellant are not affected.

Description

technical field [0001] The invention relates to a non-isocyanate curing system propellant and a preparation method thereof, belonging to the technical field of solid propellants. Background technique [0002] Advanced solid propellant technology is the core key technology of advanced strategic and tactical missile weapons and equipment, which directly determines the performance level of the missile weapon power system. With the complex and changeable battlefield environment and the diversification of war forms, the requirements for high reliability of weapon systems in future wars will continue to upgrade. Stronger environmental adaptability and more stable and reliable performance are bound to be important trends in the development of propellant technology in the future. [0003] At present, the commonly used composite solid propellants all use isocyanate as the curing agent of the propellant. However, the reaction mechanism of the isocyanate curing system is affected by m...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C06B45/10C06B33/14C06B33/12C06B33/08C06B33/06C06B33/04C08F8/00C08F220/44C08F220/14C08F220/20
CPCC06B33/04C06B33/06C06B33/08C06B33/12C06B33/14C06B45/10C08F8/00C08F220/44C08F220/14C08F220/20
Inventor 李伟杨品高王艳萍唐泉王小英刘雄尹欣梅汪越
Owner HUBEI INST OF AEROSPACE CHEMOTECHNOLOGY
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